Download or read book Numerical Investigation Into Vortical Flow about a Delta wing Configuration Up to Incidences at which Vortex Breakdown Occurs in Experiment written by J. I. van den Berg and published by . This book was released on 1994 with total page 17 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Numerical Investigation Into Vortical Flow about a Delta wing Configuration Up Ti Incidences at which Vortex Breakdown Occurs in Experiment written by J. I. Van den Berg and published by . This book was released on 1994 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1995 with total page 542 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book International Aerospace Abstracts written by and published by . This book was released on 1999 with total page 1016 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Applied Mechanics Reviews written by and published by . This book was released on 1995 with total page 694 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Government Reports Announcements Index written by and published by . This book was released on 1995 with total page 534 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aeronautical Engineering written by and published by . This book was released on 1991 with total page 538 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book 91 0744 91 0769 written by and published by . This book was released on 1991 with total page 322 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book A Digital Particle Image Velocimetry Investigation of Delta Wing Vortex Flow and Vortex Breakdown written by Jeremy David Wimer and published by . This book was released on 2003-01-01 with total page 128 pages. Available in PDF, EPUB and Kindle. Book excerpt: The vortical flow over the suction side of a 650 sweep delta wing at high angles of attack is investigated in the University of Washington water tunnel using digital particle image velocimetry (DPIV). The method is first validated and then used to qualitatively and quantitatively describe the development of the leading edge vortex (LEV) both upstream and downstream of vortex breakdown. The circulation and azimuthal velocity profile in the vortex are measured and reveal that the maximum circulation of the LEV increases nearly linearly in the downstream direction up to the point of vortex breakdown. Circulation and velocity measurements in the solid-body rotational part of the LEV core, however, reveal that once the core is formed near the apex of the wing, the circulation there remains constant until just prior to breakdown, and no further vorticity is added to the core from the shear layer. The secondary vortex is found to be the key player in separating the primary vortex core from the shear layer. This model of the flow field contradicts the generally accepted conical nature of delta wing flow. Current vortex breakdown suppression methods are analyzed in light of this new model. A numerical simulation based on the vortex filament method is also used to further the self-induction theory of vortex breakdown.

Download or read book Technical Abstract Bulletin written by Defense Documentation Center (U.S.) and published by . This book was released on 1961-10 with total page 1540 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book The Aeronautical Journal written by and published by . This book was released on 2005 with total page 700 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book 32nd Aerospace Sciences Meeting Exhibit 94 0610 94 0639 written by and published by . This book was released on 1994 with total page 466 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Vortex Flow Behavior Over Slender Delta Wing Configurations written by Xing Z. Huang and published by Springer Verlag. This book was released on 2008-10-01 with total page 516 pages. Available in PDF, EPUB and Kindle. Book excerpt: The book discusses the behavior of vortices over sharp and highly swept wing configurations used for current and future military aircraft. Special attention is paid to the effects of critical flow phenomenon such as vortex breakdown occuring at high angles of attack or high angular rates. The wind tunnel experiments conducted on delta-wing configurations in wind tunnels in Canada, Europe, Russia and the United States are given in eight chapters. The experiments provide an extended data base that gives insight into the effects of the angle of attack, angular rate, Reynolds number and Mach number on the behavior of vortices over several slender delta wings in stationary and instationary flights. A critical assessment is given in a separated chapter of the available experimental data bases and out of these data, one and the same data set is selected for the validation and verification of analytical and numerical solutions.Comprehansive computational results are given in another ten chapters. Steady-state and time-accurate solutions for the steady and unsteady flow over the selected delta-wing configuration are discussed. These solutions are generated using structured and unstructured grid methods.The analytical solutions for the flow over a delta wing are discussed and compared with experimental data in three more chapters.In the final chapter a validation and verification of the analytical and CFD solutions is given.

Download or read book Experimental and Numerical Investigation of the Vortex Flow Over a Sharp Edged Delta Wing with and Without Sideslip written by S. H. J. Naarding and published by . This book was released on 1988 with total page 224 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Numerical Investigation of Vortex Breakdown Over A 70 Degree Delta Wing Using an Euler Code written by Magnus Tormalm and published by . This book was released on 1995 with total page 74 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Journal of Aircraft written by and published by . This book was released on 2009 with total page 760 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Time Accurate Euler Calculations of Vortical Flow Over a Delta Wing in Rolling Motion written by and published by . This book was released on 2003 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper presents the results of research conducted by Alenia (Italy), Dasa (Germany), DERA (United Kingdom), NLR (The Netherlands), and DLR (Goettingen, Germany) as part of the Western European Armaments Group (WEAG) TA15 program, Common Exercise V. The WEAG TA15 program was a collaborative program concerned with the investigation of steady and unsteady vortical flows over military aircraft configurations. An important component of the program were the Common Exercises (CE), which promoted the exchange of knowledge between the participating nations and aided the development of computational methods to predict vortical flows. As the analysis of flow fields about rolling delta wings is of high interest, the last CE of this group concentrated on the numerical and experimental investigation of unsteady flow over a 65 degree swept delta wing in rolling motion at transonic speed. Guided by previous work on unsteady motions, the numerical investigation was again restricted to unsteady Euler methods. Each participant for the numerical calculations was asked to perform unsteady Euler calculations for given test cases using a mandatory grid and a given number of physical time steps per period. Numerical calculations with different unsteady Euler methods using a common grid were performed at a constant rolling rate of omega(r)=0.0762 for different angles of incidence: alpha(sub 0)=0 degrees, alpha(sub 0)=10 degrees, and alpha(sub 0)=17 degrees. The numerical results reveal that the different spatial discretizations lead to characteristic differences mainly in the magnitudes of the vortex-induced suction peaks in the unsteady pressure distributions and in the prediction of vortex breakdown. The results should finally result in the development of a data base for further code validation. (13 figures, 14 refs.).